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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 100,000
Max Cl/Cd: 58.69 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3025-il-100000-n5.txt
Download as CSV file: xf-s3025-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3366   0.09121   0.08648  -0.0339   1.0000   0.0503
  -7.750  -0.3393   0.08848   0.08383  -0.0340   1.0000   0.0504
  -7.500  -0.3444   0.08588   0.08133  -0.0338   1.0000   0.0501
  -7.250  -0.3534   0.08346   0.07902  -0.0330   1.0000   0.0498
  -7.000  -0.3606   0.08081   0.07648  -0.0329   1.0000   0.0493
  -6.750  -0.3684   0.07783   0.07359  -0.0333   1.0000   0.0483
  -6.250  -0.3532   0.06174   0.05731  -0.0487   0.9901   0.0245
  -6.000  -0.3269   0.05645   0.05189  -0.0549   0.9816   0.0237
  -5.750  -0.2976   0.05022   0.04541  -0.0618   0.9731   0.0228
  -5.500  -0.2705   0.04419   0.03902  -0.0668   0.9626   0.0218
  -5.250  -0.2418   0.03866   0.03301  -0.0708   0.9532   0.0218
  -5.000  -0.2092   0.03422   0.02799  -0.0741   0.9459   0.0228
  -4.750  -0.1802   0.03070   0.02385  -0.0756   0.9363   0.0234
  -4.500  -0.1462   0.02752   0.02006  -0.0774   0.9298   0.0236
  -4.250  -0.1164   0.02513   0.01718  -0.0779   0.9204   0.0238
  -4.000  -0.0842   0.02308   0.01468  -0.0786   0.9124   0.0242
  -3.750  -0.0513   0.02141   0.01267  -0.0792   0.9045   0.0249
  -3.500  -0.0213   0.01997   0.01109  -0.0796   0.8954   0.0260
  -3.250   0.0122   0.01896   0.00998  -0.0806   0.8881   0.0290
  -3.000   0.0411   0.01812   0.00900  -0.0806   0.8775   0.0332
  -2.750   0.0712   0.01724   0.00804  -0.0809   0.8683   0.0379
  -2.500   0.1024   0.01639   0.00708  -0.0812   0.8595   0.0488
  -2.250   0.1297   0.01546   0.00645  -0.0811   0.8488   0.1134
  -2.000   0.1563   0.01437   0.00622  -0.0813   0.8392   0.3093
  -1.750   0.1834   0.01361   0.00597  -0.0811   0.8300   0.4808
  -1.500   0.2043   0.01287   0.00589  -0.0789   0.8193   0.6896
  -1.250   0.2668   0.01225   0.00551  -0.0843   0.8130   0.9780
  -1.000   0.3016   0.01226   0.00524  -0.0856   0.8023   1.0000
  -0.750   0.3274   0.01233   0.00508  -0.0851   0.7912   1.0000
  -0.500   0.3538   0.01241   0.00494  -0.0847   0.7809   1.0000
  -0.250   0.3805   0.01248   0.00482  -0.0843   0.7710   1.0000
   0.000   0.4056   0.01259   0.00477  -0.0836   0.7598   1.0000
   0.250   0.4314   0.01271   0.00473  -0.0831   0.7493   1.0000
   0.500   0.4577   0.01281   0.00468  -0.0826   0.7394   1.0000
   0.750   0.4833   0.01294   0.00468  -0.0821   0.7286   1.0000
   1.000   0.5087   0.01308   0.00472  -0.0815   0.7176   1.0000
   1.250   0.5345   0.01321   0.00475  -0.0809   0.7071   1.0000
   1.500   0.5607   0.01334   0.00476  -0.0804   0.6971   1.0000
   1.750   0.5857   0.01349   0.00487  -0.0798   0.6854   1.0000
   2.000   0.6110   0.01365   0.00496  -0.0792   0.6741   1.0000
   2.250   0.6366   0.01380   0.00506  -0.0786   0.6631   1.0000
   2.500   0.6624   0.01395   0.00516  -0.0780   0.6521   1.0000
   2.750   0.6875   0.01412   0.00529  -0.0774   0.6402   1.0000
   3.000   0.7125   0.01430   0.00545  -0.0768   0.6280   1.0000
   3.250   0.7376   0.01447   0.00562  -0.0762   0.6158   1.0000
   3.500   0.7627   0.01465   0.00581  -0.0755   0.6035   1.0000
   3.750   0.7877   0.01484   0.00599  -0.0749   0.5908   1.0000
   4.000   0.8125   0.01503   0.00617  -0.0742   0.5776   1.0000
   4.250   0.8371   0.01523   0.00638  -0.0735   0.5637   1.0000
   4.500   0.8615   0.01544   0.00663  -0.0728   0.5490   1.0000
   4.750   0.8855   0.01566   0.00688  -0.0720   0.5333   1.0000
   5.000   0.9093   0.01590   0.00715  -0.0712   0.5167   1.0000
   5.250   0.9328   0.01615   0.00745  -0.0703   0.4993   1.0000
   5.500   0.9560   0.01643   0.00773  -0.0694   0.4812   1.0000
   5.750   0.9789   0.01673   0.00805  -0.0684   0.4622   1.0000
   6.000   1.0012   0.01706   0.00842  -0.0675   0.4420   1.0000
   6.250   1.0231   0.01744   0.00881  -0.0664   0.4217   1.0000
   6.500   1.0445   0.01785   0.00925  -0.0653   0.3994   1.0000
   6.750   1.0652   0.01831   0.00971  -0.0641   0.3773   1.0000
   7.000   1.0853   0.01881   0.01023  -0.0629   0.3540   1.0000
   7.250   1.1048   0.01937   0.01078  -0.0615   0.3315   1.0000
   7.500   1.1235   0.01999   0.01143  -0.0602   0.3089   1.0000
   7.750   1.1418   0.02064   0.01210  -0.0588   0.2869   1.0000
   8.000   1.1589   0.02137   0.01282  -0.0572   0.2651   1.0000
   8.250   1.1756   0.02211   0.01360  -0.0557   0.2431   1.0000
   8.500   1.1900   0.02297   0.01443  -0.0539   0.2188   1.0000
   8.750   1.2028   0.02391   0.01534  -0.0520   0.1925   1.0000
   9.000   1.2141   0.02495   0.01629  -0.0500   0.1643   1.0000
   9.250   1.2239   0.02609   0.01734  -0.0479   0.1373   1.0000
   9.500   1.2314   0.02730   0.01845  -0.0456   0.1138   1.0000
   9.750   1.2389   0.02852   0.01965  -0.0432   0.0930   1.0000
  10.000   1.2443   0.02994   0.02103  -0.0407   0.0761   1.0000
  10.250   1.2481   0.03154   0.02263  -0.0383   0.0591   1.0000
  10.500   1.2489   0.03343   0.02451  -0.0358   0.0468   1.0000
  10.750   1.2482   0.03553   0.02668  -0.0335   0.0386   1.0000
  11.000   1.2459   0.03786   0.02901  -0.0316   0.0342   1.0000
  11.250   1.2467   0.04003   0.03137  -0.0300   0.0309   1.0000
  11.500   1.2458   0.04247   0.03395  -0.0288   0.0287   1.0000
  11.750   1.2419   0.04534   0.03691  -0.0278   0.0269   1.0000
  12.000   1.2376   0.04838   0.04008  -0.0271   0.0260   1.0000
  12.250   1.2358   0.05135   0.04325  -0.0266   0.0251   1.0000
  12.500   1.2333   0.05448   0.04657  -0.0263   0.0242   1.0000
  12.750   1.2309   0.05773   0.05000  -0.0261   0.0235   1.0000
  13.000   1.2285   0.06108   0.05351  -0.0262   0.0230   1.0000
  13.250   1.2261   0.06453   0.05712  -0.0264   0.0224   1.0000
  13.500   1.2237   0.06808   0.06082  -0.0267   0.0219   1.0000
  13.750   1.2210   0.07176   0.06467  -0.0272   0.0214   1.0000
  14.000   1.2183   0.07553   0.06858  -0.0278   0.0210   1.0000
  14.250   1.2148   0.07952   0.07268  -0.0287   0.0205   1.0000
  14.500   1.2106   0.08367   0.07694  -0.0296   0.0199   1.0000
  14.750   1.2060   0.08819   0.08166  -0.0310   0.0196   1.0000
  15.000   1.2004   0.09306   0.08676  -0.0327   0.0193   1.0000
  15.250   1.1927   0.09844   0.09238  -0.0350   0.0190   1.0000
  15.500   1.1835   0.10428   0.09844  -0.0376   0.0187   1.0000
  15.750   1.1728   0.11066   0.10504  -0.0409   0.0185   1.0000
  16.000   1.1613   0.11747   0.11206  -0.0445   0.0184   1.0000
  16.250   1.1479   0.12500   0.11979  -0.0488   0.0183   1.0000
  16.500   1.1333   0.13317   0.12815  -0.0537   0.0184   1.0000
  16.750   1.1167   0.14231   0.13746  -0.0593   0.0185   1.0000
  17.000   1.0984   0.15245   0.14776  -0.0656   0.0188   1.0000
  17.250   1.0788   0.16371   0.15914  -0.0726   0.0191   1.0000
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